EP0971241B1 - Digitales Weltraumfahrzeugantennen-Nachführsystem - Google Patents
Digitales Weltraumfahrzeugantennen-Nachführsystem Download PDFInfo
- Publication number
- EP0971241B1 EP0971241B1 EP99113213A EP99113213A EP0971241B1 EP 0971241 B1 EP0971241 B1 EP 0971241B1 EP 99113213 A EP99113213 A EP 99113213A EP 99113213 A EP99113213 A EP 99113213A EP 0971241 B1 EP0971241 B1 EP 0971241B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- tracking
- incident signal
- spacecraft
- signal
- received
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 230000004044 response Effects 0.000 claims description 42
- 239000013598 vector Substances 0.000 claims description 14
- 238000000034 method Methods 0.000 claims description 11
- 238000013461 design Methods 0.000 description 4
- 230000015556 catabolic process Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010606 normalization Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/26—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/12—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave
- H01Q19/17—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source comprising two or more radiating elements
Definitions
- the present invention generally relates to spacecraft antenna tracking systems, and more particularly to spacecraft antenna tracking systems which can be used in conjunction with shaped or parabolic reflector antenna elements.
- a spacecraft antenna tracking system has been analog based.
- Antenna tracking systems are e.g. known from Jp-abstracts vol. 016, no.355 (30 July 1992) or vol. 018, no.005 (7 January 1994).
- Such analog tracking systems typically consist of one or more arrays of feeds and a beam forming network (BFN) that are used in conjunction with a spacecraft reflector antenna system and connected to a modulator assembly (MA) and an analog tracking control receiver (TCR). Location of the elements in the feed array and the design of the BFN cause the reflector antenna system to produce a sum beam, and a null beam.
- BFN beam forming network
- the MA compares the phase and amplitude response of the sum beam to the phase and amplitude responses of the null beams and produces an amplitude modulated signal.
- the amplitude modulated signal is demodulated by the analog TCR and appropriate spacecraft control voltages are produced in response thereto.
- the present invention provides a digital spacecraft antenna tracking system having at least one shaped antenna element positioned on the spacecraft to receive an incident signal transmitted from a ground station, and a tracking array comprising a plurality of array antenna elements oriented relative to the at least one reflector antenna element. Each of the plurality of array antenna elements generates an output signal corresponding to the received incident signal.
- a tracking control receiver is connected to the output signals, and comprises a memory for storing a set of predetermined responses generated by a plurality of reference incident signals having a known direction relative to a reference grid.
- a processor is arranged to compare the output signals to the set of predetermined responses and determine the direction of the received incident signal based on the comparison.
- the present invention further provides a method for tracking the direction of an incident signal transmitted by a ground station and received by a spacecraft antenna tracking system comprising positioning at least one reflector antenna element on the spacecraft to receive the incident signal, and orienting a tracking array comprising a plurality of array antenna elements relative to the antenna reflector element so that each of the plurality of array antenna elements generates an output signal corresponding to the received incident signal.
- a set of predetermined responses generated by a plurality of reference incident signals having a known direction relative to a reference grid are stored in a memory, and compared to the output signals to determine the direction of the received incident signal.
- the direction of a beacon signal incident on the spacecraft reflector antenna system can be obtained by the tracking control receiver (TCR) by comparing the response to the beacon signal with the stored set of premeasured responses. Once the direction of the signal is obtained, the TCR assigns control voltages which are used by the spacecraft to steer the spacecraft antenna to a desired pointing direction relative to the beacon signal.
- a multiplexer is connected to each of the plurality of array antenna elements for multiplexing the output signals into a single channel prior to processing by the tracking control receiver.
- the Figure is a block diagram of a digital spacecraft antenna tracking system in accordance with the present invention.
- a digital spacecraft antenna tracking system 10 is integrated into a payload and operating system of a spacecraft 12.
- the spacecraft includes at least one shaped or parabolic reflector 14, a communication feed or feed array 16, and a plurality of feed elements 18 surrounding the communication feed 16 to form a tracking array.
- the remaining details regarding spacecraft 12 which are not related to tracking system 10 are otherwise conventional in arrangement and operation.
- the tracking array feeds 18 are connected to a mixer/multiplexer (M/MUX) 20 via respective coaxial cables or waveguides 22.
- M/MUX 20 is connected to a digital tracking control receiver (TCR) 24 via a coaxial cable 26 and a control harness 28.
- TCR 24 utilizes a microprocessor 30 and a programmable memory 32 as described in more detail below.
- a signal 34 from a beacon located on the ground is reflected off of the shaped (or parabolic) reflector 14 (or multiple reflectors) and received by the elements 18 in the tracking array.
- the signal received by each element in the tracking array is transmitted to the M/MUX 20 through the waveguides 22.
- the M/MUX mixes the signals down to an intermediate frequency (IF) and multiplexes the signals so they can be transmitted over a single channel.
- the multiplexed signal is amplified and transmitted to the TCR 24 through coaxial'cables 26.
- Timing and local oscillator (LO) signals are transmitted between the digital TCR and M/MUX by the wire harness 28.
- the digital TCR is arranged to demultiplex the signal and obtain the relative phase and amplitude response of each element 18 in the tracking array.
- the beacon direction is obtained by correlating the beacon responses to a lookup table of responses to signals from known directions stored in memory 32. Once the beacon direction is obtained, TCR 24 assigns steering control voltages that are transmitted to the spacecraft control system by a wire harness 36.
- correlation between a calibrated tracking array response and the tracking array response to an arbitrary incident signal is obtained by taking the dot product between the eight dimensional vectors formed by the i and q responses of the four antenna elements 18 in the tracking array. Pointing errors are bounded by the angular distance between points used to calibrate the tracking array.
- the phase and amplitude for each element 18 in the tracking array is read corresponding to a signal generated from each direction having a predetermined orientation with respect to a reference grid that defines the tracking region, such as a 41 x 41 grid.
- a reference grid that defines the tracking region
- the reference response vectors must be normalized by the response of at least one of the horns. In this case, the normalization is with respect to the vector sum of all the horn responses:
- the reference vector terms are stored in memory 32 along with the corresponding grid directions (az i ,el i ).
- a dot product is taken between the set of eight-dimensional reference response vectors and the eight-dimensional response vector for the signal incident from within the tracking region.
- the tracking system of the present invention exhibits superior performance compared to conventional "sum and difference" tracking systems, and does not require a beam forming network. Further, the digital tracking system of the present invention does not experience degradation when used with shaped reflector antenna systems, and produces a linear response over a greater angular region than is possible with conventional analog tracking systems. Finally, efficiency in memory use can be increased by concentrating the calibration points near the area of interest and using sparse coverage for other directions, possibly extending to the edge of the geosphere.
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Aerials With Secondary Devices (AREA)
Claims (16)
- Digitales Weltraumfahrzeug-Antennen-Nachführsystem mit:zumindest einem Reflektorantennenelement (14), das auf dem Weltraumfahrzeug positioniert ist, um ein einfallendes, von einer Bodenstation übertragenes Signal zu empfangen;einer Nachführanordnung, die eine Vielzahl von Gruppenantennenelementen (18) aufweist, die relativ zu dem zumindest einen geformten Antennenelement (14) ausgerichtet sind, wobei jedes der Vielzahl von Gruppenantennenelementen (18) ein Ausgangssignal (22) entsprechend dem empfangenen einfallenden Signal (34) erzeugt; undeinem Nachführsteuerempfänger (24), der auf jedes Ausgangssignal der Vielzahl von Gruppenantennenelementen anspricht, dadurch gekennzeichnet, daß der Nachführsteuerempfänger (24) einen Speicher (32) zum Speichern einer Menge von vorbestimmten Antworten, die von einer Vielzahl von einfallenden Referenzsignalen mit bekannter Richtung relativ zu einem Referenzgitter erzeugt werden, und einen Prozessor (30) aufweist, der hergerichtet ist, um die Ausgangssignale mit der Menge von vorbestimmten Antworten zu vergleichen und die Richtung des empfangenen einfallenden Signals basierend auf dem Vergleich zu bestimmen.
- System nach Anspruch 1, dadurch gekennzeichnet, daß der Nachführsteuerempfänger (24) hergerichtet ist, um eine Amplitude und eine Phase jedes Ausgangssignals eines Gruppenantennenelements in jeweilige i- und q-Term für jedes empfangene einfallende Signal umzuwandeln.
- System nach Anspruch 2, dadurch gekennzeichnet, daß die Menge von vorbestimmten Antworten eine Menge von Referenzantwortvektoren aufweist, die aus den umgewandelten i- und q-Termen für jedes Ausgangssignal der Vielzahl von Antennenelementen (18) gebildet ist, und daß der Prozessor (30) eingerichtet ist, um ein Skalarprodukt zwischen jedem i- und q-Term für ein empfangenes einfallendes Signal und jeden Referenzantwortvektor zu bilden.
- System nach Anspruch 3, dadurch gekennzeichnet, daß die Richtung des empfangenen einfallenden Signals als die Richtung des Referenzgitters bestimmt wird, für die das Skalarprodukt ein Maximum ist.
- System nach einem der vorhergehenden Ansprüche, gekennzeichnet durch einen Multiplexer (20), der mit jedem der Vielzahl von Gruppenantennenelementen (18) verbunden ist, um die Ausgangssignale in einen einzelnen Kanal für den Nachführempfänger (24) zu multiplexen.
- System nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Nachführsteuerempfänger (24) ferner eingerichtet ist, um eine Verstellsteuerspannung (36) zur Verwendung durch ein Weltraumfahrzeug-Steuersystem in Antwort auf die festgelegte Richtung des empfangenen einfallenden Signals zu erzeugen.
- System nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß zumindest ein Reflektorantennenelement eine Parabolantenne (14) aufweist.
- System nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das empfangene einfallende Signal (34) ein Baken-Signal aufweist.
- System nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß zumindest ein Reflektorantennenelement ein Antennenelement mit geformtem Reflektor aufweist.
- Verfahren zum Verfolgen der Richtung eines einfallenden Signals, das von einer Bodenstation übertragen wird und von einem Weltraumfahrzeug-Antennen-Nachführsystem (10) empfangen wird, mit:Positionieren von zumindest einem Reflektorantennenelement (14) auf dem Weltraumfahrzeug, um das einfallende Signal (34) zu empfangen;Ausrichten einer Nachführanordnung mit einer Vielzahl von Gruppenantennenelementen (18) relativ zu zumindest einem Reflektorantennenelement (14), so daß jedes der Vielzahl von Gruppenantennenelementen ein Ausgangssignal (22) entsprechend dem empfangenen einfallenden Signal erzeugt;Speichern in einem Speicher (32) einer Menge von vorbestimmten Antworten, die von einer Vielzahl von einfallenden Referenzsignalen mit bekannter Richtung relativ zu einem Referenzgitter erzeugt werden;Vergleichen der Ausgangssignale mit der Menge von vorbestimmten Antworten; undBestimmen der Richtung des empfangenen einfallenden Signals (34) auf der Basis des Vergleichs.
- Verfahren nach Anspruch 10, gekennzeichnet durch: Umwandeln einer Amplitude und einer Phase des Ausgangssignals jedes Gruppenantennenelements in jeweilige i- und q-Terme für das empfangene einfallende Signal (34).
- Verfahren nach Anspruch 10 oder 11, dadurch gekennzeichnet, daß die Menge von vorbestimmten Antworten eine Menge von Referenzantwortvektoren aufweist, die aus der Umwandlung eines i- und q-Terms der Amplitude und Phase jedes Ausgangssignals der Vielzahl von Antennenelementen (18) in Antwort auf die einfallenden Signale mit bekannter Richtung gebildet werden, und daß das Vergleichen der Ausgangssignale mit der Menge der vorbestimmten Antworten das Erzeugen eines Skalarprodukts zwischen jedem i- und q-Term für ein empfangenes einfallendes Signal und jeden Referenzantwortvektor aufweist.
- Verfahren nach Anspruch 12, dadurch gekennzeichnet, daß die Richtung des empfangenen einfallenden Signals als Richtung des Referenzgitters festgelegt wird, für die das Skalarprodukt maximal ist.
- Verfahren nach einem der Ansprüche 10 bis 13, gekennzeichnet durch Erzeugen einer Verstellsteuerspannung (36) zur Verwendung durch einem Weltraumfahrzeug-Steuersystem in Antwort auf die festgelegte Richtung des empfangenen einfallenden Signals.
- Verfahren nach einem der Ansprüche 10 bis 14, gekennzeichnet durch ein Steigern der Speicherverwendungseffizienz durch Konzentrieren der bekannten Richtung relativ zu dem Referenzgitter nahe den einfallenden Referenzsignalen auf ein Gebiet bestimmten Interesses.
- Verfahren nach einem der Ansprüche 10 bis 15, gekennzeichnet durch Multiplexen (20) der Ausgangssignale jedes der Vielzahl von Gruppenantennenelementen in einen einzelnen Kanal vor dem Vergleich der Ausgangssignale mit der Menge der vorbestimmten Antworten.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE69900353T DE69900353T3 (de) | 1998-07-10 | 1999-07-08 | Digitales Weltraumfahrzeugantennen-Nachführsystem |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US112851 | 1987-10-23 | ||
US09/112,851 US5926130A (en) | 1998-07-10 | 1998-07-10 | Digital spacecraft antenna tracking system |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0971241A1 EP0971241A1 (de) | 2000-01-12 |
EP0971241B1 true EP0971241B1 (de) | 2001-10-17 |
EP0971241B2 EP0971241B2 (de) | 2011-08-17 |
Family
ID=22346176
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99113213A Expired - Lifetime EP0971241B2 (de) | 1998-07-10 | 1999-07-08 | Digitales Weltraumfahrzeugantennen-Nachführsystem |
Country Status (3)
Country | Link |
---|---|
US (1) | US5926130A (de) |
EP (1) | EP0971241B2 (de) |
DE (1) | DE69900353T3 (de) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6393255B1 (en) * | 1999-08-11 | 2002-05-21 | Hughes Electronics Corp. | Satellite antenna pointing system |
US6288671B1 (en) * | 2000-04-25 | 2001-09-11 | Hughes Electronics Corporation | Beacon-assisted spacecraft attitude control systems and methods |
US6695262B2 (en) | 2001-12-07 | 2004-02-24 | The Boeing Company | Spacecraft methods and structures for enhanced service-attitude accuracy |
US7154439B2 (en) * | 2003-09-03 | 2006-12-26 | Northrop Grumman Corporation | Communication satellite cellular coverage pointing correction using uplink beacon signal |
US20050068228A1 (en) * | 2003-09-25 | 2005-03-31 | Burchfiel Jerry D. | Systems and methods for implementing vector models for antenna communications |
DE602008002715D1 (de) | 2007-03-03 | 2010-11-04 | Astrium Ltd | Satelliten-strahlrichtfehlerkorrektur in einer digitalen strahlformungsarchitektur |
AU2020222983A1 (en) * | 2019-02-12 | 2021-07-29 | Viasat Inc. | Ultra-low cost high performance satellite aperture |
CN113949437B (zh) * | 2021-09-18 | 2024-03-26 | 西安空间无线电技术研究所 | 一种基于信道模拟技术的中继捕跟外场试验模拟系统及方法 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IT1199172B (it) * | 1984-07-27 | 1988-12-30 | Selenia Ind Elettroniche | Sistema per il controllo fine del puntamento di antenne con sensore a radio frequenza,ad ampio campo di acquisizione angolare |
CA1318394C (en) † | 1988-04-12 | 1993-05-25 | Ryuichi Hiratsuka | Antenna apparatus and attitude control method |
US5321410A (en) † | 1988-06-09 | 1994-06-14 | Southwest Research Institute | Adaptive doppler DF system |
JP2941391B2 (ja) * | 1990-08-29 | 1999-08-25 | 株式会社東芝 | アンテナ駆動装置 |
JPH05249217A (ja) * | 1992-03-05 | 1993-09-28 | Clarion Co Ltd | 受信装置のアンテナ追尾制御装置 |
US5402132A (en) † | 1992-05-29 | 1995-03-28 | Mcdonnell Douglas Corporation | Monopole/crossed slot single antenna direction finding system |
US5274382A (en) * | 1992-07-06 | 1993-12-28 | Datron Systems, Incorporated | Antenna system for tracking of satellites |
JP2944408B2 (ja) * | 1994-01-24 | 1999-09-06 | 日本電気株式会社 | 移動体搭載アンテナの制御装置及び制御方法 |
US5754139A (en) * | 1996-10-30 | 1998-05-19 | Motorola, Inc. | Method and intelligent digital beam forming system responsive to traffic demand |
-
1998
- 1998-07-10 US US09/112,851 patent/US5926130A/en not_active Expired - Lifetime
-
1999
- 1999-07-08 EP EP99113213A patent/EP0971241B2/de not_active Expired - Lifetime
- 1999-07-08 DE DE69900353T patent/DE69900353T3/de not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
US5926130A (en) | 1999-07-20 |
DE69900353T3 (de) | 2012-02-02 |
DE69900353D1 (de) | 2001-11-22 |
EP0971241B2 (de) | 2011-08-17 |
EP0971241A1 (de) | 2000-01-12 |
DE69900353T2 (de) | 2002-05-02 |
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